CN111917458A - Space data processing node device based on CCSDS specification - Google Patents
Space data processing node device based on CCSDS specification Download PDFInfo
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- CN111917458A CN111917458A CN202010789522.XA CN202010789522A CN111917458A CN 111917458 A CN111917458 A CN 111917458A CN 202010789522 A CN202010789522 A CN 202010789522A CN 111917458 A CN111917458 A CN 111917458A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/30—Circuit design
- G06F30/34—Circuit design for reconfigurable circuits, e.g. field programmable gate arrays [FPGA] or programmable logic devices [PLD]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/30—Circuit design
- G06F30/36—Circuit design at the analogue level
- G06F30/373—Design optimisation
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/30—Monitoring; Testing of propagation channels
- H04B17/309—Measuring or estimating channel quality parameters
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/30—Monitoring; Testing of propagation channels
- H04B17/382—Monitoring; Testing of propagation channels for resource allocation, admission control or handover
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18517—Transmission equipment in earth stations
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L9/00—Cryptographic mechanisms or cryptographic arrangements for secret or secure communications; Network security protocols
- H04L9/06—Cryptographic mechanisms or cryptographic arrangements for secret or secure communications; Network security protocols the encryption apparatus using shift registers or memories for block-wise or stream coding, e.g. DES systems or RC4; Hash functions; Pseudorandom sequence generators
- H04L9/0618—Block ciphers, i.e. encrypting groups of characters of a plain text message using fixed encryption transformation
Abstract
The invention relates to the technical field of spatial data processing, and provides a spatial data processing node device based on a CCSDS specification. The method comprises the following steps: the forward link baseband processing module is used for finishing the baseband data processing functions of the forward link, including data caching, state monitoring, frame conformity detection, channel receiving processing and data output processing; the return link baseband processing module is used for finishing the baseband data processing functions of the return link, including data caching, channel multiplexing, data routing, packet analysis, service data priority scheduling, safety processing, flow control and channel sending processing; and the parameter configuration and health telemetering module is used for completing the functions of parameter configuration and health telemetering management through a bus. The space data processing node device based on the CCSDS specification is designed and completed by adopting the programmable logic FPGA, the direct transmission of the space data is realized, the protocol overhead is saved, and the processing delay of the data is reduced.
Description
Technical Field
The invention relates to the technical field of spatial data processing, in particular to a spatial data processing node device based on a CCSDS specification.
Background
With the development of aerospace technology, aerospace tasks are increasingly complex, and the requirements for satellite networking and interconnection are increasing. The current space-based network mostly refers to the ground mature TCP/IP network standard, and the TCP/IP protocol cluster has high requirements on the stability and the connectivity of the network; due to sparsity, high mobility and limited communication range of the satellite, a continuous, stable and end-to-end path often does not exist, and in addition, the spatial link has the characteristics of high error code, high time delay and asymmetric link bandwidth, so that the TCP/IP is not suitable for message transmission in the spatial link.
On the other hand, the information transmission generally adopts the CCSDS (conditional Committee for Space Data Systems, international Space Data system counseling Committee) protocol specification in the Space segment, and if the satellite and the ground both adopt the TCP/IP protocol, customized equipment needs to be added to complete the conversion between the CCSDS protocol and the TCP/IP protocol. In addition, the overhead of the TCP/IP protocol is high, and precious bandwidth resources of the space link are greatly wasted. And most satellite networks belong to small sparse networks, and the advantage of realizing a TCP/IP protocol in a satellite system is insufficient.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a spatial data processing node device based on the CCSDS specification, which utilizes the source aircraft identifier, the virtual channel identifier, and the insertion information (including the target aircraft identifier, the transmission channel, and the lifecycle) in the CCSDS protocol specification to complete routing and security management of spatial link data, supports flexible configuration of on-orbit service parameters, and can satisfy inter-satellite communication of a small satellite network.
The above object of the present invention is achieved by the following technical solutions:
a space data processing node device based on CCSDS specification adopts a Programmable logic FPGA (Field Programmable Gate Array, a product further developed on the basis of Programmable devices such as PAL, GAL and the like) which is used as an Application Specific Integrated Circuit (ASIC, an Application Specific Integrated Circuit, an Integrated Circuit designed and manufactured according to the requirements of Specific users and Specific electronic systems), and the space data processing based on the CCSDS specification comprises a forward link baseband processing module, a return link baseband processing module and a parameter configuration and health remote measuring module;
the forward link baseband processing module is used for finishing the baseband data processing functions of the forward link, including data caching, state monitoring, frame conformance detection, channel receiving processing and data output processing;
the return link baseband processing module is used for finishing the baseband data processing functions of the return link, including data caching, channel multiplexing, data routing, packet analysis, service data priority scheduling, safety processing, flow control and channel sending processing;
and the parameter configuration and health telemetering module is used for completing the functions of parameter configuration and health telemetering management through a bus.
Further, the spatial data processing node device based on the CCSDS specification further includes:
the spatial data conforms to the CCSDS specification and inserts information including a target aircraft identification, a sending node identification, and a message lifecycle into an insert field of a CCSDS frame format.
Further, the forward link baseband processing module further includes:
the forward link data caching unit is used for receiving data by adopting a double-port RAM in the FPGA, discarding and processing the detected illegal CCSDS frame and giving remote measurement;
a forward link state monitoring unit for completing the real-time monitoring of the CCSDS data frame synchronization head, the frame length and the link state of the forward link and sending the detection result to the parameter configuration and monitoring telemetering module;
the forward link frame conformance detection unit is used for reading a source aircraft identifier in a CCSDS frame, rejecting the CCSDS frame with the same identifier as the satellite aircraft identifier, avoiding data loop formation, reading a virtual channel identifier of the CCSDS frame, and rejecting an idle frame and a link test frame;
and the forward link channel processing unit is used for completing channel processing functions including channel decoding and channel decryption according to the satellite application requirements, and the channel processing functions are expanded in a form including XMC daughter cards.
Further, the return link baseband processing module further includes:
the return link channel multiplexing unit is used for carrying out channel multiplexing on N paths of CCSDS data frames output after being processed by the forward link baseband processing module or/and 1 path of CCSDS data frames sent to the spatial link by the satellite according to a link priority relation table;
the return link port routing unit is used for reading the satellite aircraft identifier, the node identifier, the port routing matrix and the target aircraft identifier in the CCSDS frame, analyzing the channel multiplexing data and distributing the channel multiplexing data to the satellite users;
the return link routing unit is used for reading the local satellite aircraft identifier, the node identifier, the link routing matrix and the target aircraft identifier in the CCSDS frame and routing the data after channel multiplexing;
the backward link service classification unit is used for reading the virtual channel identifier in the CCSDS frame after the link routing and performing classification and caching according to a service classification table for representing the degree of service;
the return link information safety control unit is used for reading the target aircraft identifier in the CCSDS frame format and rejecting the CCSDS frame with the same identifier as the local satellite aircraft; reading the life cycle, and if the life cycle is 0, rejecting the CCSDS frame; if the life cycle is not 0, the life cycle is decreased once;
the return link flow control unit is used for carrying out priority transmission according to the transmission link rate specified in the service classification table and sequentially transmitting high-priority service data, medium-priority service data and low-priority service data;
and the return link channel processing unit is used for finishing channel processing functions including channel coding and channel encryption according to the satellite application requirements, and the channel processing functions are expanded in a form including the XMC daughter card.
Further, the link priority relationship table, the port routing matrix, the link routing matrix and the service classification table support on-track updating of the link priority relationship table, the port routing matrix, the link routing matrix and the service classification table through the parameter configuration and health telemetry module.
Further, the sending link rate of the return link supports on-track updating of the return link through the parameter configuration and health telemetry module.
Further, when the bandwidth of the return link is insufficient, the low priority service data, the medium priority service data and the high priority service data are discarded in sequence according to the service classification table;
when the bandwidth of the return link has a margin, idle frames are inserted to keep the channel continuous.
Furthermore, the XMC daughter card for channel processing completes encryption and decryption algorithms with different strengths and coding and decoding algorithms with different error correction capabilities according to the actual application requirements of the satellite.
Further, the parameter configuration and health telemetry module collects health telemetry information of the forward link state monitoring unit, the forward link frame conformity detection unit, the return link information security control unit and the return link flow control unit, packages the health telemetry information and sends the health telemetry information to the bus, and the health telemetry information is arbitrated by the bus controller.
Further, the health telemetry information includes identifying continuity of a forward link input clock, correctness of a forward link input frame format, legitimacy of a return link output frame format, and a return link output traffic status.
Compared with the prior art, the invention has at least one of the following beneficial effects:
(1) the space link channel processing based on the CCSDS specification is finished by adopting the design of a programmable logic array (FPGA), an additional conversion device is not needed, and the space link channel processing can be directly used for space transmission, so that the protocol overhead is saved, and the processing delay of data is reduced.
(2) The forward link and the return link are completely independent in baseband processing, the application requirement of asymmetric space link bandwidth is met, and the energy efficiency ratio of satellite application is improved.
(3) The forward link and the return link adopt XMC daughter card design for channel processing, thereby realizing coding and decoding algorithms with different error correction capabilities, encryption and decryption algorithms with different strengths, and the like, and improving the generalization degree of the node device.
Drawings
FIG. 1 is a diagram illustrating an overall structure of a spatial data processing node apparatus according to the CCSDS specification;
FIG. 2 is a schematic block diagram of a spatial data processing node apparatus based on the CCSDS specification according to the present invention;
fig. 3 is a spatial data frame format based on the CCSDS specification.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
Examples
As shown in the block diagram of fig. 1 and the schematic block diagram of fig. 2, the present embodiment provides a spatial data processing node device based on the CCSDS specification, which is implemented by using an antifuse FPGA (AX2000-CG624M) of the ACTEL corporation, and includes three parts, namely a spatial data forward link baseband processing module 1, a return link baseband processing module 2, and a parameter configuration and health telemetry module 3 based on the CCSDS specification.
The forward link baseband processing module 1 is configured to complete baseband data processing functions including data buffering, state monitoring, frame conformance detection, channel receiving processing (including channel decoding, decryption, and the like), and data output.
The return link baseband processing module 2 is configured to complete baseband data processing functions of the return link, including data caching, channel multiplexing, data routing, packet parsing, service data priority scheduling, security processing, flow control, and channel sending processing (including channel coding, encryption, and the like).
And the parameter configuration and health telemetering module 3 is used for completing the functions of parameter configuration and health telemetering management through a bus.
In the embodiment, the partition storage of the return link data is completed by using an external SDRAM (synchronous dynamic random access memory); the external MRAM is adopted to complete the storage of the link priority relation table, the port routing matrix and the link routing matrix, and the on-orbit updating is supported; and storing the source aircraft identifier, the node identifier, the initial link priority relation table, the initial port routing matrix and the initial link routing matrix by adopting the PROM.
In this embodiment, the format of the CCSDS frame is as shown in fig. 3, the frame length is 1024 bytes, the frame header is 0x1ACFFC1D, the source aircraft identifier and the target aircraft identifier are 1 byte, and the node identifier and the life cycle are 4 bits.
In this embodiment, the forward link data caching unit 11 is configured to complete data reception by using a dual-port RAM inside an FPGA, discard a detected illegal CCSDS frame, and provide telemetry.
The forward link state monitoring unit 12 is configured to determine whether a synchronization header of a CCSDS data frame is 0x1ACFFC1D, whether a frame length of a virtual channel unit is 892 bytes, and whether a frame length of a coding region is 128 bytes; and identifying the continuity of the input clock, and sending the monitoring result to the parameter configuration and monitoring telemetry module 3.
The forward link frame conformance detection unit 13 is configured to read a source aircraft identifier in a CCSDS frame, and reject a CCSDS frame having the same identifier as the satellite aircraft, thereby avoiding data looping; reading the virtual channel identification of the CCSDS frame, and eliminating idle frames and link test frames; the virtual channel identifications of the idle frame and the link test frame are set to '11111', '000000', respectively.
The forward link channel processing unit 14 completes LDPC channel decoding and block encryption algorithm channel decryption; the LDPC decoding is completed by adopting an XQ5VFX130T of Xilinx company, and the decryption of the XMC daughter card core processor by adopting an AX2000 of ACTEL company through a block encryption algorithm;
in this embodiment, the return link channel multiplexing unit 21 is configured to perform channel multiplexing on N channels of CCSDS data frames output after being processed by the forward link baseband processing module and/or 1 channel of CCSDS data frames sent by the satellite to the spatial link according to the link priority relationship table; in this embodiment, the default link priority relationship table is shown in table 1.
Table 1 link priority relationship table
The return link port routing unit 22 is configured to read the local satellite aircraft identifier, the node identifier, the port routing matrix, and the target aircraft identifier in the CCSDS frame, and distribute the data multiplexed by the channels to the local satellite users after analyzing the data.
The return link routing unit 23 is configured to read the local aircraft identifier, the node identifier, the link routing matrix, and the target aircraft identifier in the CCSDS frame, and route the data after channel multiplexing.
The backward link service classification unit 24 is configured to read a virtual channel identifier in a CCSDS frame after the link routing, and perform classification and caching according to a service classification table (service urgency) of the service.
The return link information safety control unit 25 is configured to read a target aircraft identifier in a CCSDS frame format, and reject a CCSDS frame having the same identifier as the local satellite aircraft; reading the life cycle, and if the life cycle is 0, rejecting the CCSDS frame; if the life cycle is not 0, the life cycle is decremented once.
The return link flow control unit 26 is configured to perform priority transmission at a specified transmission link rate according to the service classification table, and sequentially transmit high-priority service data, medium-priority service data, and low-priority service data.
The return link channel processing unit 27 is configured to complete LDPC channel coding and block encryption algorithm channel encryption functions according to a satellite application requirement, where the LDPC coding XMC daughter card core processor is completed by using AX2000 of ACTEL corporation, and the block encryption algorithm encryption XMC daughter card core processor is completed by using AX2000 of ACTEL corporation.
The parameter configuration and health telemetry module 3 collects health telemetry information of the forward link state monitoring unit 12, the forward link frame conformity detection unit 13, the return link information safety control unit 25 and the return link flow control unit 26, packages the health telemetry information and sends the health telemetry information to the RS485 bus, and then carries out arbitration by the bus controller.
In this embodiment, the health telemetry information includes identification of continuity of a forward link input clock, correctness of a forward link input frame format, legality of a return link output frame format, and a return link output link traffic status.
In this embodiment, the link priority relationship table, the port routing matrix, and the link routing matrix support in-orbit injection updating, for a satellite whose network topology and data type need to be changed during a flight mission, the in-orbit injection can be performed through the bus, the parameter configuration module in the node controller performs instruction analysis and then executes, and updates the parameters to the dynamic parameter storage area.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
It should be noted that the above embodiments can be freely combined as necessary. The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A space data processing node device based on CCSDS specifications is characterized in that a programmable logic FPGA is adopted, and space data processing based on CCSDS specifications comprises the following steps: a forward link baseband processing module, a return link baseband processing module and a parameter configuration and health remote measuring module;
the forward link baseband processing module is used for finishing the baseband data processing functions of the forward link, including data caching, state monitoring, frame conformance detection, channel receiving processing and data output processing;
the return link baseband processing module is used for finishing the baseband data processing functions of the return link, including data caching, channel multiplexing, data routing, packet analysis, service data priority scheduling, safety processing, flow control and channel sending processing;
and the parameter configuration and health telemetering module is used for completing the functions of parameter configuration and health telemetering management through a bus.
2. The CCSDS specification-based spatial data processing node arrangement of claim 1 further comprising:
the spatial data conforms to the CCSDS specification and inserts information including a target aircraft identification, a sending node identification, and a message lifecycle into an insert field of a CCSDS frame format.
3. The CCSDS specification-based spatial data processing node arrangement of claim 1 or 2, wherein said forward link baseband processing module further comprises:
the forward link data caching unit is used for receiving data by adopting a double-port RAM in the FPGA, discarding and processing the detected illegal CCSDS frame and giving remote measurement;
a forward link state monitoring unit for completing the real-time monitoring of the CCSDS data frame synchronization head, the frame length and the link state of the forward link and sending the detection result to the parameter configuration and monitoring telemetering module;
the forward link frame conformance detection unit is used for reading a source aircraft identifier in a CCSDS frame, rejecting the CCSDS frame with the same identifier as the satellite aircraft identifier, avoiding data loop formation, reading a virtual channel identifier of the CCSDS frame, and rejecting an idle frame and a link test frame;
and the forward link channel processing unit is used for completing channel processing functions including channel decoding and channel decryption according to the satellite application requirements, and the channel processing functions are expanded in a form including XMC daughter cards.
4. The CCSDS specification-based spatial data processing node arrangement of claim 3 wherein said return link baseband processing module further comprises:
the return link channel multiplexing unit is used for carrying out channel multiplexing on N paths of CCSDS data frames output after being processed by the forward link baseband processing module or/and 1 path of CCSDS data frames sent to the spatial link by the satellite according to a link priority relation table;
the return link port routing unit is used for reading the satellite aircraft identifier, the node identifier, the port routing matrix and the target aircraft identifier in the CCSDS frame, analyzing the channel multiplexing data and distributing the channel multiplexing data to the satellite users;
the return link routing unit is used for reading the local satellite aircraft identifier, the node identifier, the link routing matrix and the target aircraft identifier in the CCSDS frame and routing the data after channel multiplexing;
the backward link service classification unit is used for reading the virtual channel identifier in the CCSDS frame after the link routing and performing classification and caching according to a service classification table for representing the degree of service;
the return link information safety control unit is used for reading the target aircraft identifier in the CCSDS frame format and rejecting the CCSDS frame with the same identifier as the local satellite aircraft; reading the life cycle, and if the life cycle is 0, rejecting the CCSDS frame; if the life cycle is not 0, the life cycle is decreased once;
the return link flow control unit is used for carrying out priority transmission according to the transmission link rate specified in the service classification table and sequentially transmitting high-priority service data, medium-priority service data and low-priority service data;
and the return link channel processing unit is used for finishing channel processing functions including channel coding and channel encryption according to the satellite application requirements, and the channel processing functions are expanded in a form including the XMC daughter card.
5. The CCSDS specification based spatial data processing node arrangement of claim 4 wherein said link priority relationship table, said port routing matrix, said link routing matrix, said traffic classification table support on-track updating thereof by said parameter configuration and health telemetry module.
6. The CCSDS specification based spatial data processing node arrangement of claim 4 wherein a return link transmit link rate supports on-track updating thereof by said parameter configuration and health telemetry module.
7. The CCSDS specification-based spatial data processing node arrangement of claim 4 wherein when bandwidth of a return link is insufficient, said low priority traffic data, said medium priority traffic data and said high priority traffic data are discarded in sequence according to said traffic classification table;
when the bandwidth of the return link has a margin, idle frames are inserted to keep the channel continuous.
8. The spatial data processing node device according to claim 3 or 4, wherein said XMC daughter card for channel processing implements different strength encryption/decryption algorithms and different error correction capability coding/decoding algorithms according to the actual application requirements of the satellite.
9. The spatial data processing node apparatus according to claim 4, wherein the parameter configuration and health telemetry module collects health telemetry information of the forward link status monitoring unit, the forward link frame conformance detection unit, the return link information security control unit, and the return link flow control unit, packages the health telemetry information to the bus, and sends the health telemetry information to the bus controller for arbitration.
10. The CCSDS specification-based spatial data processing node arrangement of claim 9 wherein said health telemetry information comprises identifying continuity of forward link input clock, correctness of forward link input frame format, legitimacy of return link output frame format and return link output traffic status.
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| CN113300756A (en) * | 2021-05-24 | 2021-08-24 | 上海航天电子通讯设备研究所 | Intersatellite link mesh routing system based on CCSDS specification |
| CN114422024A (en) * | 2022-04-01 | 2022-04-29 | 深圳航天东方红卫星有限公司 | Satellite-ground closed loop high-reliability data transmission method |
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